Stall flutter is a nonlinear aeroelastic phenomenon that can affect several types of aeroelastic systems such as
helicopter rotor blades, wind turbine blades, and highly flexible wings. Although the related aerodynamic
phenomenon of dynamic stall has been the subject of many experimental studies, stall flutter itself has rarely been
investigated. This paper presents a set of experiments conducted on a NACA0012 airfoil undergoing stall flutter
oscillations in a low-speed wind tunnel. The aeroelastic responses are analyzed with the objective of characterizing
the local bifurcation behavior of the system. It is shown that symmetric stall flutter oscillations are encountered as a
result of a subcritical Hopf bifurcation, followed by a fold bifurcation. The cause of these bifurcations is the
occurrence of dynamic stall, which allows the transfer of energy from the freestream to the wing. A second
bifurcation occurs at the system’s static divergence airspeed. As a consequence, the wing starts to undergo
asymmetric stall flutter bifurcations at only positive (or only negative) pitch angles. The dynamic stall mechanism
itself does not change but the flow only separates on one side of the wing.